Flying machine



Dec. 27, 1932. w MESSERSCHMH'T 1,891,941

FLYING MACHINE 'Filed Feb. 19, 1930 2 Sheets-Sheet 2 znvez far: .Z Y-i Patented Dec. 27, 1932 UNITED STATES WILLY IESSERBCHMIT'I', O1 AUGSBUBG, GERMANY FLYING MACHINE Application fled February 18, 1880, Serial 110. 429,604, and in Germany l'ebruary 28, 1929.

My invention relates to flying machines and more particularly to the connection of the wings with the fuselage.

It is an object of my invention to reduce the number of fittings required for this connection. In the flying machines as hitherto designed four or more fittings are provided which require very exact workmanship and involve a considerable increase in weight.

In order to overcome these drawbacks I provide fittings at three points only, two'of them being arranged at the end of the front spar, the third at some distance to the rear. The two fittings in front absorb the bending stresses while the third fitting at the rear absorbsthe foreand aft-forces and the torsional stresses.

My invention may be ada ted to wings with a front and rear spar, an to wings with a front spar only. In the latter case a bracing which will be referred to as the auxiliary spar is provided, extending between the front spar and the rear fitting.

In the drawings affixed to this specifica- :5 tion and forming part thereof, flying machines having the arrangement of fittings embodying my invention are illustrated dia-.

grammatically by way of example.

In the drawings Fig. 1 is a diagrammatic elevation of'a flying machine with wings having a front and a rear spar,

Fig. 2 is a plan view of one of the wings and the adjacent part of the fuselage,

machine with wings having a front spar and an auxiliary spar,

Fig. 4 is a plan view of one of the Wings and the adjacent part of the fuselage,

Fig. 5 shows the parts illustrated in Fig. 4 drawn to a larger scale,

Fig. 6 is a section on the line VI-VI in Fig. 5, i

Fig. 7 is a section on the line VIIVII in Fig. 5 and Fig. 8 is a section on the line VIIIVIII of Fig. 5. 7

Referring to the drawings, 1 is the fuselage, 2 is one of the wings, 3 is the front Fig. 3 is a diagrammatic elevation of a spar with the fittings 7 and 8, and 4 is the rear spar.

Referring more particularly to Fig. 1, the wing 2 is equip ed with a front spar 3 and a F rear spar 4. he front spar 3 is provided D with the usual upper and lower flanges 5 and 6, with the fitting 7 at the top, and the fitting 8 at the bottom, Fig. 7, and corresponding fittings 9 and' 10 are provided on a frame or bulkhead 11 of the fuselage 1. The rear spar G0 4 is provided with a single fitting 12.

F1 3, 5 and 8 show a wing having only the ront spar 3. Here the third fitting 12 is attached to an auxiliary spar 13 which extends from the front spar to the fitting and is built-up from two struts, each extending across a bay between two of the wing ribs 14.

As it is desirable that the auxiliary spar 13 should not be too stiff, it is connected to the front spar 3 at the third rib 14. As it is also desirable that the connection of the auxiliary spar 13 with the second rib 14 should be in t e axis of the wing, it is kinked so that its point of intersection with the second rib lies 1n the plane of the axis 15, as shown in Figs. 4 and 5. Obviously the auxiliary spar may be so arranged as to extend throughany numllgeipf bays and may be designed without any Fig. 8 shows the bracing of the auxilia spar 13, 16 and 17 being diagonal wires whic are attached to the fitting 12 at 18 and 19. Instead, of braces a built-up girder similar to the front spar 3 might be provided to form 833 the. auxiliary spar. This spar may even be built-up altogether from dia onal wires such as 16 and 17, without any girder parts.

The fittings 9 and 10 at the frame or bulkhead 11 are secured to transverse struts 20 and 21 of the frame or bulkhead 11 by rivets 22. The fittings 7 and 8 may be connected with the respective flanges by rivets 23-. or by screws. 24 is the inner end wall of th'e wing and 25 is the cover of the fuselage.

I wish it to be understood that desire to be limited to the exact details of construction shown and described for obvious modifications will occur to a person skilled in the art.

In the claims aflixed to this specification 100 I do not no selection of any particular modification of the invention is intended to the exclusion of other modifications thereof and the right to subsequently make claim to any modification not covered by these claims is expressely reserved.

I claim: a I

1. A flyin machine having a fuselage, a pair of canti ever wings, a front spar in each 10 wing, two fittings for securing said wing to said fuselage spaced apart on said front spar, an auxiliary spar connected with said front spar, and a third fitting at said auxiliar spar.

2. A flying machine having a fuse age, a pair of cantilever wings, a' front spar in each wing, two fittings for securing said wing to said fuselage spaced apart on said front spar, an auxiliary spar connected with said front spar and arranged at an angle to the axis 20 of said wing, and a third fitting at said auxiliary spar.

3. A flyin machine having a fuselage, a pair of canti ever wings, a front spar in each wing, two fittings for securing said wing to said fuselage spaced apart on said front spar, a kinked auxiliary s ar connected with said front spar, and a fitting at said auxiliary s ar.

4. A flyin machine having a fuselage, a 30 pair of canti ever wings, a front spar in each wing, two fittings for securing said wing to said fuselage spaced apart on said front spar, an auxiliary spar consisting of bracing means connected with said front spar, and a third 35 fitting at said auxiliary spar.

In testimon whereof I afiix m signature.

WI Y MESSER HMITT. 

